Proposed Rule2026-06690
Airworthiness Directives; Bell Textron Canada Limited Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
April 7, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2025-09-03, which applies to certain Bell Textron Canada Limited (Bell) Model 430 helicopters. AD 2025-09-03 reduced the life limits on the main rotor (M/R) clevises, universal bearings, universal to pitch link bolts, the tube assembly, and the rod end assembly and requires replacing the M/R pitch link assemblies with re-identified part numbered assemblies. Since the FAA issued AD 2025-09-03, the FAA received comments proposing changes to the actions of AD 2025-09-03. This proposed AD proposes changes to actions in AD 2025-09-03 and addresses the comments received. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 66 (Tuesday, April 7, 2026)</title>
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[Federal Register Volume 91, Number 66 (Tuesday, April 7, 2026)]
[Proposed Rules]
[Pages 17610-17614]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-06690]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 91, No. 66 / Tuesday, April 7, 2026 /
Proposed Rules
[[Page 17610]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-3476; Project Identifier MCAI-2025-01366-R]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Canada Limited Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2025-09-03, which applies to certain Bell Textron Canada Limited (Bell)
Model 430 helicopters. AD 2025-09-03 reduced the life limits on the
main rotor (M/R) clevises, universal bearings, universal to pitch link
bolts, the tube assembly, and the rod end assembly and requires
replacing the M/R pitch link assemblies with re-identified part
numbered assemblies. Since the FAA issued AD 2025-09-03, the FAA
received comments proposing changes to the actions of AD 2025-09-03.
This proposed AD proposes changes to actions in AD 2025-09-03 and
addresses the comments received. The FAA is proposing this AD to
address the unsafe condition on these products.
DATES: The FAA must receive comments on this NPRM by May 22, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-3476; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI) any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For Transport Canada material identified in this AD,
contact Transport Canada, Transport Canada National Aircraft
Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, CANADA;
phone: (888) 663-3639; email: <a href="/cdn-cgi/l/email-protection#7b2f38553a12090c14090f1312151e08083f12091e180f120d1e085638141508121c151e081f1e151a0d121c1a191217120f1e552f383b0f18551c1855181a"><span class="__cf_email__" data-cfemail="d98d9af798b0abaeb6abadb1b0b7bcaaaa9db0abbcbaadb0afbcaaf49ab6b7aab0beb7bcaabdbcb7b8afb0beb8bbb0b5b0adbcf78d9a99adbaf7bebaf7bab8">[email protected]</span></a>. You may find the Transport Canada
material on the Transport Canada website at tc.canada.ca/en/aviation.
<bullet> You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of this
material at the FAA, call (817) 222-5110.
FOR FURTHER INFORMATION CONTACT: Alexis Whitaker, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY; phone:
(516) 228-7309; email: <a href="/cdn-cgi/l/email-protection#3958555c41504a1753174e51504d58525c4b795f5858175e564f"><span class="__cf_email__" data-cfemail="3b5a575e4352481551154c53524f5a505e497b5d5a5a155c544d">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under ADDRESSES. Include ``Docket No. FAA-2026-3476; Project Identifier
MCAI-2025-01366-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Alexis Whitaker, Aviation Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
The FAA issued AD 2025-09-03, Amendment 39-23024 (90 FR 17547,
April 28, 2025), (AD 2025-09-03), for Bell Model 430 helicopters,
serial numbers 49001 through 49129 inclusive. AD 2025-09-03 was
prompted by an MCAI originated by Transport Canada, which is the
aviation authority for Canada. Transport Canada issued AD CF-2024-40,
dated December 3, 2024, (Transport Canada AD CF-2024-40) to correct an
unsafe condition identified as wear and damage of the M/R clevis neck
or threaded area, which could lead to crack initiation at the M/R
clevis neck and failure of the M/R pitch link, resulting in loss of
control of the helicopter.
AD 2025-09-03 was prompted by an in-flight failure of the main
rotor pitch link clevis due to fatigue damage caused by excessive wear
of the universal bearing. AD 2025-09-03 requires a visual inspection of
the M/R clevis, rod end, and a certain part-numbered universal bearing;
performing a purge grease; performing a magnetic particle
[[Page 17611]]
inspection of each M/R clevis; and depending on the inspection results,
removing or replacing certain parts, and performing additional actions.
AD 2025-09-03 also requires recurring inspections of each M/R clevis
and each universal bearing. Additionally, AD 2025-09-03 requires
reducing the life limits of affected parts and re-identifying the M/R
pitch link assemblies with new part numbered assemblies.
The FAA issued AD 2025-09-03 to detect and address wear and damage
of the M/R pitch link assembly components. The unsafe condition, if not
addressed, could result in crack initiation at the M/R clevis neck and
failure of the M/R pitch link, which could result in loss of control of
the helicopter.
Actions Since AD 2025-09-03 Was Issued
Since the issuance of AD 2025-09-03, the FAA received comments from
Bell and Superior Aviation Services requesting changes to the required
actions of AD 2025-09-03, specifically in regard to some of the
exceptions in the regulatory text of AD 2025-09-03. The comment
disposition below specifically explains and addresses these comments.
The FAA revised some of the actions required in this proposed rule in
response to comments received on AD 2025-09-03. These revisions are
explained below in the comment disposition. You may examine the MCAI in
the AD docket at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-3476.
Comments on AD 2025-09-03
The FAA gave the public the opportunity to comment on AD 2025-09-
03. The following presents the comments received on AD 2025-09-03 and
the FAA's response to each comment.
Request To Remove the Magnetic Particle Inspection (MPI) Requirement
Bell and Superior Aviation Services requested that the FAA remove
the requirement to perform an MPI after performing each detailed visual
inspection in paragraph (h)(4) of AD 2025-09-03. The commenters stated
the addition of an MPI at every 50 hours [time-in-service] is an
unnecessary and burdensome requirement for operators due to not all
operators having readily available access to perform an MPI.
Additionally, the commenters stated all clevises were required to be
inspected using an MPI in accordance with FAA AD 2021-24-09 and any
suspected clevises would have been removed at the accomplishment of
that FAA AD. The commenters also stated that Transport Canada AD CF-
2024-40 states an MPI should only be performed if any suspected defects
are found as a result of the detailed inspection (DI). One commenter
stated difficulty in locating the procedure to perform the MPI as well
as finding individuals that are certified in performing the MPI. This
commenter suggested instead of the MPI, the FAA should require a more
thorough check (inspection) of the universal bearing by focusing on
excessive wear and rotational forces. Additionally, one commenter
stated the Transport Canada AD CF-2024-40 already requires a recurring
50-hour or 60-day DI, and the FAA AD adding an additional MPI
requirement after each DI inspection is not necessary due to the 60-day
period imposing little stress on the pitch link clevis and the
additional inspections are excessive.
The FAA agrees that performing an MPI of the universal bearings
after each DI is not a requirement of Transport Canada AD CF-2024-40.
Accordingly, the FAA has determined that performing an MPI of the
universal bearings after every DI is not necessary and has revised the
regulatory text of this proposed AD by removing this recurring
inspection. The FAA also agrees that the requirement to perform an MPI
of the M/R clevis after every DI is unnecessary to address the unsafe
condition. However, the FAA has determined that there may be limited
circumstances in which an MPI of the clevis must be performed. The FAA
revised paragraph (h)(4) of the regulatory text of this proposed AD to
require an MPI only if any linear indications are found on the M/R
clevis as a result of the DI. The FAA acknowledges that only certified
individuals can perform an MPI.
Request To Remove the Re-Identification Requirement
Bell requested that the FAA revise paragraph (h)(6) of the Required
Actions paragraph of AD 2025-09-03 that states ``Where Part I paragraph
A.9. of Transport Canada AD CF-2024-40 specifies to re-identify the
main rotor pitch link assemblies and sub-components, for this AD those
actions are not required if already accomplished when doing Part I
paragraphs A.2. through A.4. of Transport Canada AD CF-2024-40.''
Reidentification is only conducted in paragraph A.9 of Transport Canada
AD CF-2024-40. Paragraphs A.2 through A.4 specify replacing parts with
serviceable parts.
The FAA disagrees that paragraph (h)(6) of AD 2025-09-03 should be
revised. Part I paragraphs A.2 through A.4 of the Transport Canada AD
CF-2024-40 specify accomplishing the required actions in accordance
with Part I of Bell Alert Service Bulletin (ASB) 430-22-61, Basic
Issue, dated November 6, 2023 (ASB 430-22-61). Paragraphs 4.d and 8 of
Part I of ASB-430-22-61 require part number re-identification of the
universal bearing, pitch link assemblies, and their sub-components, and
the FAA has determined that this should be required in the FAA AD. No
changes were made to this proposed AD as a result of this comment.
Request To Remove the Replacement Requirement for Certain Parts
Bell requested that the FAA remove paragraph (h)(7) of AD 2025-09-
03. Bell stated that paragraph (h)(7) is not correct since Table 4-1 of
the Bell 430 ALS [Airworthiness Limitations Section] does not have a
life limit assigned to the -109 or -111 part numbers, instead it is
based on condition.
The FAA disagrees with removing paragraph (h)(7) of AD 2025-09-03
because the FAA determined this exception is necessary to clarify that
the requirement in Transport Canada AD CF-2024-40 Part I paragraph B.
does not apply to M/R pitch link assemblies part numbers 430-010-411-
109, -109FM, -111, and -111FM, as those parts are replaced on-condition
and do not have a life limit. No changes were made to this proposed AD
as a result of this comment.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Transport Canada AD CF-2024-40, which was approved
for incorporation by reference as of May 13, 2025 (90 FR 17547, April
28, 2025). Transport Canada AD CF-2024-40 specifies procedures for
verifying rotorcraft historical records to determine the total
accumulated hours air time of certain parts, replacing the M/R pitch
link assembly components that have exceeded their life limit, re-
identifying the M/R pitch link assemblies, and performing a detailed
inspection of the pitch link tube assembly, rod end assembly, and
universal pitch link bolt.
Transport Canada AD CF-2024-40 also specifies procedures for
performing repetitive detailed inspections of the M/R clevises and
universal bearings (including hardware) and depending on the inspection
results, replacing any part that does not meet inspection criteria or
further corrective actions. Additionally, Transport Canada AD CF-2024-
40 specifies procedures for
[[Page 17612]]
performing a purge grease, performing a magnetic particle inspection
and either replacing any M/R clevis with cracks or replacing any
missing cadmium plating. Furthermore, Transport Canada AD CF-2024-40
specifies reporting any cracks or M/R clevises with damage beyond
published limits to Bell Product Support Engineering.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
FAA's Determination
These products have been approved by the civil aviation authority
(CAA) of another country and are approved for operation in the United
States. Pursuant to the FAA's bilateral agreement with this State of
Design Authority, that authority has notified the FAA of the unsafe
condition described in the MCAI referenced above. The FAA is issuing
this NPRM after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.
Proposed AD Requirements in This NPRM
This proposed AD would continue to require all actions of AD 2025-
09-03, except for any changes described above to the actions specified
in Transport Canada AD CF-2024-40 and any differences identified as
exceptions in the regulatory text of this proposed AD. See
``Differences Between this Proposed AD and the MCAI'' for a discussion
of the general differences included in this proposed AD.
Differences Between This Proposed AD and the MCAI
The MCAI requires replacing M/R pitch link assembly P/Ns 430-010-
411-109, -109FM, -111, and -111FM before they exceed their life limit.
This AD does not contain that requirement because those assemblies do
not have a life limit and are replaced on-condition as required by the
Airworthiness Limitations Section.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some CAA ADs as the primary
source of information for compliance with requirements for
corresponding FAA ADs. The FAA has been coordinating this process with
manufacturers and CAAs. As a result, the FAA proposes to incorporate
Transport Canada AD CF-2024-40 by reference in the FAA final rule. This
proposed AD would, therefore, require compliance with Transport Canada
AD CF-2024-40 in its entirety through that incorporation, except for
any differences identified as exceptions in the regulatory text of this
proposed AD. Material required by Transport Canada AD CF-2024-40 for
compliance will be available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-
2026-3476 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 29 helicopters of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Review records to determine total .25 work-hour x $85 $0 $22................. $638.
time on each part. per hour = $22.
Inspect the pitch link tube 4 work-hours x $85 0 $340................ $9,860.
assembly, rod end assembly, and per hour = $340.
universal to pitch link bolt.
Inspect the M/R pitch link clevis 2 work-hours x $85 0 $170 per inspection $4,930 per
per hour = $170. cycle. inspection cycle.
Inspect the universal bearing and 2 work-hours x $85 0 $170 per inspection $4,930 per
hardware. per hour = $170. cycle. inspection cycle.
Re-identify components........... 1 work-hour x $85 0 $85................. $2,465.
per hour = $85.
Perform a magnetic particle 4 work-hours x $85 0 $340 per inspection $9,860 per
inspection. per hour = $340. cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any repairs/
replacements that would be required based on the results of the
inspection. The agency has no way of determining the number of
helicopters that might need these repairs or replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replace an M/R clevis................. 4 work-hours x $85 per $432 $772 per part.
hour = $340.
Replace a universal bearing........... 4 work-hours x $85 per 3,566 $3,906 per part.
hour = $340.
Replace a universal to pitch link bolt 4 work-hours x $85 per 374 $714 per part.
hour = $340.
Replace missing cadmium plating....... 4 work-hours x $85 per 0 $340.
hour = $340.
Replace a pitch link tube assembly or 4 work-hours x $85 per 6,463 $6,803 per part.
rod end assembly. hour = $340.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
[[Page 17613]]
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive 2025-09-03, Amendment 39-23024 (90
FR 17547, April 28, 2025); and
0
b. Adding the following new airworthiness directive:
Bell Textron Canada Limited: Docket No. FAA-2026-3476; Project
Identifier MCAI-2025-01366-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 22, 2026.
(b) Affected ADs
This AD replaces AD 2025-09-03, Amendment 39-23024 (90 FR 17547,
April 28, 2025).
(c) Applicability
This AD applies to Bell Textron Canada Limited (Bell) Model 430
helicopters, serial numbers 49001 through 49129 inclusive,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6220, Main Rotor
Head.
(e) Unsafe Condition
This AD was prompted by an in-flight failure of the main rotor
(M/R) pitch link clevis (clevis) due to fatigue damage caused by
excessive wear of the universal bearing. The FAA is issuing this AD
to detect and address wear and damage of the M/R pitch link assembly
components. The unsafe condition, if not addressed, could result in
crack initiation at the M/R clevis neck and failure of the M/R pitch
link, which could result in loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, Transport Canada AD CF-2024-40, dated December 3,
2024 (Transport Canada AD CF-2024-40).
(h) Exceptions to Transport Canada AD CF-2024-40
(1) Where Transport Canada AD CF-2024-40 refers to its effective
date, this AD requires using May 13, 2025, the effective date of AD
2025-09-03.
(2) Where Transport Canada AD CF-2024-40 requires compliance in
terms of hours air time, this AD requires using hours time-in-
service.
(3) Where Transport Canada AD CF-2024-40 uses the term ``new''
in the definition of ``serviceable part,'' this AD requires
replacing that text with ``new (zero hours time-in-service)''.
(4) Where any paragraph in Transport Canada AD CF-2024-40
specifies performing a magnetic particle inspection (MPI) ``if any
suspected defects are found'' after performing a detailed
inspection, this AD requires replacing that text with ``if any
suspected defects (evidenced by linear indications) are found on the
M/R clevis as a result of the detailed inspection''.
Note to paragraph (h)(4): a linear indication is defined as an
indication for which the longest dimension is at least three times
longer than the smallest one.
(5) Where Part I paragraph A.8. and Part III paragraph B. of
Transport Canada AD CF-2024-40 specify to purge grease the bearings,
for this AD those actions are not required if already accomplished
when doing Part I paragraph A.7 and Part III paragraph A. of
Transport Canada AD CF-2024-40.
(6) Where Part I paragraph A.9. of Transport Canada AD CF-2024-
40 specifies to re-identify the main rotor pitch link assemblies and
sub-components, for this AD those actions are not required if
already accomplished when doing Part I paragraphs A.2. through A.4.
of Transport Canada AD CF-2024-40.
(7) Where Part I paragraph B. of Transport Canada AD CF-2024-40
specifies to replace each component listed in Table 1 of the Bell
ASB before exceeding the applicable airworthiness life limit
indicated in Table 4-1 of the applicable ALS [Airworthiness
Limitations Section], for this AD that requirement does not apply to
M/R pitch link assemblies part numbers 430-010-411-109, -109FM, -
111, and -111FM, as those parts are replaced on-condition.
(i) No Reporting Requirement
Although the material referenced in Transport Canada AD CF-2024-
40 specifies to submit certain information to the manufacturer, this
AD does not require that action.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (k) of
this AD and email to: <a href="/cdn-cgi/l/email-protection#b7f6faf8f4f7d1d6d699d0d8c1"><span class="__cf_email__" data-cfemail="cd8c80828e8dabacace3aaa2bb">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Additional information
For more information about this AD, contact Alexis Whitaker,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY; phone: (516) 228-7309; email:
<a href="/cdn-cgi/l/email-protection#41202d243928326f2b6f36292835202a2433012720206f262e37"><span class="__cf_email__" data-cfemail="9bfaf7fee3f2e8b5f1b5ecf3f2effaf0fee9dbfdfafab5fcf4ed">[email protected]</span></a>.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(3) The following material was approved for IBR on May 13, 2025
(90 FR 17547, April 28, 2025).
(i) Transport Canada AD CF-2024-40, dated December 3, 2024.
(ii) [Reserved]
(4) For Transport Canada material identified in this AD, contact
Transport Canada National Aircraft Certification, 159 Cleopatra
Drive, Nepean, Ontario K1A 0N5, Canada; phone: 888-663-3639; email:
<a href="/cdn-cgi/l/email-protection#e7b3a4c9a68e95908895938f8e89829494a38e958284938e918294caa48889948e8089829483828986918e8086858e8b8e9382c9b3a4a79384c98084c98486"><span class="__cf_email__" data-cfemail="a7f3e489e6ced5d0c8d5d3cfcec9c2d4d4e3ced5c2c4d3ced1c2d48ae4c8c9d4cec0c9c2d4c3c2c9c6d1cec0c6c5cecbced3c289f3e4e7d3c489c0c489c4c6">[email protected]</span></a>. You
may find this material on the Transport Canada website at
tc.canada.ca/en/aviation.
[[Page 17614]]
(5) You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(6) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#5b3d29753235282b3e382f3234351b353a293a753c342d"><span class="__cf_email__" data-cfemail="87e1f5a9eee9f4f7e2e4f3eee8e9c7e9e6f5e6a9e0e8f1">[email protected]</span></a>.
Issued on April 2, 2026.
Paul R. Bernado,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-06690 Filed 4-6-26; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on April 7, 2026.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.